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Shock Waves pp 909-913 | Cite as

Numerical study on ignition of supersonic combustion fueled by partly catalyzed kerosene

  • S. L. Xu
  • S. H. Huang
  • X. Y. Liu
  • J. M. Dong
  • X. Z. Liu
Conference paper

Abstract

The supersonic combustion of partly catalyzed kerosene was numerically investigated in this paper. The objective is to test whether the two present ignition model can successfully initiate the chemical reactions in the combustion. Implicit LU scheme and upwind TVD scheme was used to solve the fully Navier-Stokes equations of multi-species mixture. Chemical source term was treated implicitly to avoid stiffness. 10 species/10 steps model was used to describe the chemical reaction of C2H4/O2/N2 system. The contours of pressure, temperature, and species mass fraction were numerically obtained, as well as the static pressure distribution along the walls. The results indicate that the combustion is successfully initiated. The pressure downstream the fuel strut rises continuously due to fuel air combustion. Species CO is the important interim product and species CO2 and H2O are the two distinguished combustion products. Also, the net thrust can be numerically obtained for the strut and cavity in this combustor.

Keywords

Fuel Injector Symmetrical Plane Static Pressure Distribution Supersonic Combustion Cavity Floor 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

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    R.A. Mercier, T.F.M. Ronald: US air force hypersonic technology program, AIAA paper (1996)Google Scholar
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    A. Jameson, S. Yoon: Lower-upper implicit schemes with multiple grid for the Eulerian equations. AIAA J 25(7), 929 (1987)ADSCrossRefGoogle Scholar
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    H.C. Yee: Upwind and symmetric shock-capturing schemes. NASA 89464 (1987)Google Scholar
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    R.A. Baurle, Mathur, M.R. Gruber, K.R. Jackson: A numerical and experimental investigation of a scramjet combustor for a hypersonic missile applications. AIAA 98-3121 (1998)Google Scholar

Copyright information

© Tsinghua University Press and Springer-Verlag Berlin Heidelberg 2005

Authors and Affiliations

  • S. L. Xu
    • 1
  • S. H. Huang
    • 1
  • X. Y. Liu
    • 2
  • J. M. Dong
    • 2
  • X. Z. Liu
    • 2
  1. 1.Dept. of Mechanics and Mech. Eng.University of Science and Technology of ChinaHefeiChina
  2. 2.Research Institute of PropulsionChinese Aerospace Scientific and Technological Co.BeijingChina

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